Results
91-14-07: 91-14-07 SAAB-SCANIA: Amendment 39-7048. Docket No. 91-NM-48-AD. Applicability: Certain Model SAAB 340B series airplanes, as listed in SAAB Service Bulletin 340-52-013, Revision 1, dated December 18, 1990, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of the forward toilet service door during flight, and subsequent damage to the propeller, wing, or empennage, accomplish the following: A. Within 500 hours time-in-service after the effective date of this AD, perform a one-time inspection for correct installation of the hinge pin, in accordance with SAAB Service Bulletin 340-52-013, Revision 1, December 18, 1990, and accomplish the following: 1. If the hinge pin is installed correctly, prior to further flight, replace the latches and reinforce the forward toilet service door in accordance with the service bulletin. 2. If the hinge pin is installed incorrectly, prior to further flight, replace the latches, reinforce the forward toilet service doors, remove the hinge pin, and repair and reinstall the hinge pin, in accordance with the service bulletin. B. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. D. The inspection, repair, replacement, and reinforcement requirements shall be done in accordance with SAAB Service Bulletin 340-52-013, Revision 1, dated December 18, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from SAAB-Scania AB, Product Support, S- 581.88, Linkoping, Sweden. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7048, AD 91-14-07) becomes effective on August 6, 1991.
2011-13-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: An investigation into the loss of a TRU during landing has revealed that this incident was preceded by the detachment of the TRUs fixed structure front ring rivet lines on the rear flange. It was concluded that the loss of rivet lines was directly associated with a previous translating cowl gearbox stubshaft fracture and the subsequent repair of the fixed structure to Engine Manual repair No. FRS5887. This repair instructs the replacement of the damaged section of the structure but does not require the rivets adjacent to the repair to be replaced although latest analysis has shown that the rivets may have weakened as a result of a translating cowl gearboxstubshaft failure. We are issuing this AD to prevent failure of the attachment rivets resulting in loss of engine structural integrity, which may result in release of the thrust reverser unit from the engine.
84-08-02 R1: 84-08-02 R1 CESSNA: Amendment 39-4981. Applies to Cessna Model 650 airplanes S/N 650- 0001 thru 650-0035 certificated in all categories. To prevent possible engine flameout, accomplish the following unless already accomplished. A. Prior to the next flight fabricate a placard which reads as follows: "INDICATED FUEL LESS THAN 200 POUNDS PER WING FUEL TANK IS UNUSABLE" and operate the airplane in accordance with this limitation. This placard should be fabricated of .032-inch minimum thickness aluminum or plastic material with minimum 1/8-inch high stamped or engraved letters. Install the placard on the instrument panel immediately above the engine instruments centered above the fuel quantity indicator. B. Insert a copy of this airworthiness directive (AD) in the Airplane Flight Manual Section II adjacent to page 2-9. Retain this AD in the Flight Manual until superseded. C. Upon accomplishment of Cessna Service Bulletin SB 650-28-8 (fuel tank inspection) and determination that total trapped and unusable fuel weight is 85 pounds or less, the above required placard and flight manual insertion may be removed and an airplane log book entry denoting AD compliance made. D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, FAA Aircraft Certification Office, Wichita, Kansas. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Citation Marketing Division, Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas. This amendment becomes effective January 28, 1985. It was effective earlier to all recipients of airmail letter AD T84-08-02, dated April 17, 1984.
96-18-22: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 96-18-22 which was sent previously to all known U.S. owners and operators of Robinson Helicopter Company (Robinson) Model R44 helicopters by individual letters. This AD requires an inspection of the mating surfaces of the main rotor gearbox (gearbox) components for pitting, elongated bolt holes, or machining grooves, and replacement of the gearbox if elongated bolt holes, machining grooves, or an improper amount of pitting is discovered; and replacement of the 18 bolts and washers that attach the gear to the gear carrier assembly (gear carrier). This amendment is prompted by an inflight failure of the gearbox on a French-registered Model R44 helicopter that resulted in an accident. The actions specified by this AD are intended to prevent loosening of the bolts securing the gear to the gear carrier, which could lead to fatigue failure of the gear carrier within the gearbox, andsubsequent loss of power to the main rotor which could lead to a forced landing.
96-20-07: This amendment supersedes Airworthiness Directive (AD) 82-07-03, which currently requires repetitively testing (pressure decay) the combustion tube of JanAero Devices B-Series combustion heaters, Models B1500, B2030, B3040, and B4050, that are installed on aircraft, and overhauling any heater that does not pass one of these pressure decay tests. This action retains the pressure decay test and possible heater overhaul requirements of AD 82-07-03; and requires repetitive operational testing of the combustion air pressure switch, and replacing any combustion pressure switch that does not pass one of these tests. Two occurrences of failure of the affected heaters prompted this action. In one case, an explosion resulted and the baggage compartment door was blown off the airplane. In the other case, a fire occurred in the baggage compartment while the airplane was in flight. The actions specified by this AD are intended to prevent an airplane fire or explosion caused by failure of the heater combustion tube assembly or combustion air pressure switch.
74-14-01: 74-14-01 HARTZELL PROPELLERS: Amendment 39-1883 as amended by Amendment 39-1924. Applies to Hartzell T10173H()+(), T10176H()+(), T10178H()-(), and () T10282H()+() hard alloy type blades installed on but not limited to Model HC-B3TN-2( ), HC- B3TN-3( ), HC-B3TN-5( ), HC-B3TN-7( ), HC-B3TF-7( ), HC-B4TN-3( ) and HC-B4TN-5( ) propellers which are used on United Aircraft of Canada Limited PT-6A-( ) and AiResearch TPE 331( )-( ) series engines. These propellers are installed on but not limited to Swearingen SA-226 Series, Short SC-7 Series 3, Aero Commander 690 Series and de Havilland DHC-6 300 type aircraft. Compliance required as indicated, unless already accomplished. Propellers with more than 1000 hours in service, excepting those with replacement blades having less than 1000 hours in service, as of the effective date of this Airworthiness Directive are excluded. Also, the following propellers having the serial numbers listed below are excluded: PROPELLER MODEL - HC-B3TN-2; S/N - AG-275 and above PROPELLER MODEL - HC-B3TN-3; S/N - BU-4624 and above PROPELLER MODEL - HC-B3TN-5: S/N - BV-2210, BV-2213, BV-2214, BV-2216 and above PROPELLER MODEL - HC-B3TN-7: S/N - CV-7 and above PROPELLER MODEL - HC-B3TF-7: S/N - EX-3 and above PROPELLER MODEL - HC-B4TN-3: S/N - EA-255 and above PROPELLER MODEL - HC-B4TN-5: S/N - CD-62 and above To detect blade cracks and prevent possible blade failures, accomplish the following: (a) Propellers with less than 950 hours in service since new as of the effective date of this Airworthiness Directive must be inspected in accordance with Paragraph (e), within the next 50 hours time in service. (b) Propellers with 950 hours in service, but not more than 1000 hours in service as of the effective date of this Airworthiness Directive must be inspected in accordance with Paragraph (e) prior to the accumulation of 1000 hours in service. (c) Propellers whose total hours in service are unknown willbe assumed to have less than 950 hours in service since new and thus must be inspected in accordance with the requirements of Paragraph (a). (d) In the event propellers with more than 1000 hours in service are equipped with replacement blades which have less than 1000 hours in service, such propeller blades must be inspected in accordance with the requirements of Paragraphs (a) or (b), as applicable contingent upon the time in service of the replacement blades. (e) Inspect blades for cracks or defects in accordance with Hartzell Bulletin No. 105 dated May 22, 1974, or later Federal Aviation Administration approved revision, or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. Replace any cracked or defective blades before further flight with blades to which this Airworthiness Directive does not apply, or have been inspected in accordance with this Airworthiness Directive and found satisfactory. (f) Upon request of the operator a Federal Aviation Administration Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration Great Lakes Region, may adjust the compliance time specified in Paragraph (b), if the request contains substantiating data to justify the adjustment for that operator. Amendment 39-1883 became effective as of July 2, 1974. This Amendment 39-1924 becomes effective August 22, 1974.
2011-13-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Several cases of Gas Generator (GG) Turbine Blade rupture occurred in service on ARRIEL 2 twin engine applications and recently one on a single engine helicopter. For the case occurring in flight on a single engine helicopter (ARRIEL 2B1 engine), the pilot performed an emergency autorotation, landing the helicopter without further incident. We are issuing this AD to prevent rupture of a GG turbine blade, which could result in an uncommanded in-flight shutdown and an emergency autorotation landing or accident.
96-20-06: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Jetstream Model 4101 airplanes, that currently requires inspection to determine the number of hours time-in-service on the landing gear control unit, and modification of the cable (electrical wiring circuit) of the landing gear control unit. That AD was prompted by a report of failure of a micro-switch in the landing gear control unit. This amendment requires installation of a new landing gear control unit. This amendment also expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent uncommanded retraction of a landing gear, which could adversely affect airplane controllability.
96-19-18: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA Groupe AEROSPATIALE (Socata) TBM 700 airplanes. This action requires installing four rivets on the right side of the rudder and drilling drainage holes at the areas of the elevators and rudder. Reports of water accumulating in the areas of the elevators and rudder and a report of a bonding defect between the skin and rudder rear spar on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent the wing skin and the rear spar from becoming unbonded or water accumulating in either the elevators or rudder, which could result in loss of control of the airplane.
47-41-04: 47-41-04 BELL: (Was Mandatory Note 16 of AD-1H-2.) Applies to Models 47B and 47B3 Helicopters. Compliance required not later than next 50-hour transmission teardown inspection after December 1, 1947. To improve attachment of the inner race bearing on the bottom of the main rotor mast and to prevent possible chipping, the lower mast plug should incorporate a bolted retaining washer. (Bell Service Bulletin 47C41 dated June 26, 1947, covers the detail installation.)
91-12-05: 91-12-05 GENERAL DYNAMICS (CONVAIR): Amendment 39-7016. Docket No. 90-NM-289-AD. Applicability: Model 340, 440, and C131, B, C, D, E, and F (Military) series airplanes, including all airplanes converted to turbopropeller power, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of the elevator hinge pins, accomplish the following: A. Within 50 hours time-in-service or 60 days after the effective date of this AD, whichever occurs first, remove the elevator and conduct a visual inspection of the elevator hinge pins and bearings, in accordance with Part I of the Accomplishment Instructions of General Dynamics, Convair Division Service Bulletin 640 (340D) 55-5, dated September 21, 1990 (hereinafter referred to as "SB 55-5"). NOTE: Inspections previously accomplished in accordance with the Accomplishment Instructions of Alert Service Bulletin 640 (340D) 55-A5, dated March 1, 1990, are considered to comply with the requirements of this AD. B. Any hinge pins, bushings, or tapered bushings found which do not conform to the dimensional limitations specified in Part I of SB 55-5, must be replaced prior to further flight. C. Any cracked bearing plate assemblies or nut assemblies, and any loose, chattering, dry, or seized bearings, P/N AN201KP10A, must be replaced prior to further flight. D. When the elevator is reinstalled, determine if proper mating of the tapered bushing and pin surfaces exists, in accordance with Part I of SB 55-5. If proper mating does not exist, the pin must be reworked prior to further flight, in accordance with Part II of SB 55-5. E. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles ACO. The inspection and repair requirements shall be done in accordance with General Dynamics, Convair Division Service Bulletin 640 (340D) 55-5, dated September 21, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from General Dynamics, Convair Division, P.O. Box 85377, San Diego, California 92138, Attention: Chief, Aircraft Logistical Support, Mail Zone 92-2920. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7016, AD 91-12-05) becomes effective on July 25, 1991.
83-05-06: 83-05-06 AEROSPATIALE (formerly SUD): Amendment 39-4579. Applies to all Caravelle SE-210 Models III and VIR airplanes, certificated in all categories. 1. To prevent structural failures, accomplish the following within the time in service or number of flights specified in each paragraph below after the effective date of this AD, unless already accomplished. A. Compliance required in accordance with SUD Service Bulletin 32-86, Revision 7, and/or in accordance with SUD Service Bulletin 32-106, Revision 4, as noted; (1) Replace P/N 210.41.10.011-01 main landing gear hinge shaft aft end screws with P/N 210.41.10.100-01 screws (Service Bulletin 32-86) or with P/N 210.41.10.652-01 screws and 210.41.10.648-01 plugs (Service Bulletin 32-106) within the next 500 landings. (2) Inspect P/N 210.41.10.100-01 screws in accordance with Service Bulletin 32-86 within the next 500 landings or within 8,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings. (3) Inspect P/N 210.41.10.652-01 screws in accordance with Service Bulletin 32-106 within the next 500 landings or within 10,000 total landings, whichever occurs later, and thereafter at intervals not to exceed 5,000 landings. B. Compliance required in accordance with SUD Service Bulletin No. 57-40, Revision 10; (1) Inspect the lower wing center junction fitting I3 and I5 bores for corrosion, ovalization, or cracks within the next 200 hours time in service or within 15,000 hours total time in service, whichever occurs later, and thereafter at intervals not to exceed 10,500 hours time in service for airplanes with a maximum takeoff weight of 52 tons or less and 4,000 hours time in service for airplanes with a maximum takeoff weight of over 52 tons. (2) Inspect the lower wing center junction fitting I1, I2, and I4 bores for corrosion, ovalization, or cracks within the next 200 hours time in service or within 18,000 hours total time service, whichever occurs later, and thereafter at intervals not to exceed 8,000 hours time in service. (3) Repair or replace fittings per the service bulletin instructions. C. Inspect wing rib 44 upper cap fittings within the next 200 landings in accordance with SUD Service Bulletin 57-47, Revision 6. If no cracks are found, reinspect at intervals not to exceed 2,000 landings thereafter. If cracks are found, repair as necessary per the service bulletin and reinspect at intervals not to exceed 1,000 landings thereafter. 2. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). This amendment becomes effective April 11, 1983.
2021-26-22: The FAA is superseding Airworthiness Directive (AD) 2020-20-13 for certain General Electric Company (GE) CF6-80A and CF6-80C model turbofan engines. AD 2020-20-13 required ultrasonic inspection (UI) of high-pressure turbine (HPT) stage 1 and stage 2 disks and replacement of any HPT stage 1 or stage 2 disk that fails the inspection. This AD was prompted by an uncontained failure of an HPT stage 2 disk and the manufacturer's subsequent determination to expand the population of affected HPT disks requiring UI inspection. This AD requires UI of HPT stage 1 and stage 2 disks and replacement of any HPT stage 1 or stage 2 disk that fails the inspection. This AD also expands the applicability to include an additional population of affected HPT stage 1 and 2 disks requiring UI inspection. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-23: The FAA is adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. (type certificate previously held by Raytheon Aircraft Company, Hawker Beechcraft Corporation, and Beechcraft Corporation) (Textron) Model 300, 300LW, B300, and B300C airplanes. This AD was prompted by a report of a timing issue where the yaw servo software can generate a motor position fault when the pilot applies rudder input at the same time the rudder boost system is activated, which disables the rudder boost function and leads to a reduced ability of the flight crew to maintain the safe flight and landing of the airplane or loss of control of the airplane. This AD requires updating the software version of the yaw servo. The FAA is issuing this AD to address the unsafe condition on these products.
96-19-10: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767 series airplanes. This action requires a one-time inspection to detect discrepancies of the main battery shunt, and replacement with a serviceable part, if necessary. This action also requires inspection of certain wires, washers, and brass jam nuts to detect any discrepancy, and replacement with a serviceable part, if necessary. Additionally, this action requires inspection, and adjustment if necessary, of the torque and resistance of the installation of the main battery ground stud. This amendment is prompted by reports of interruptions of electrical power during flight due to improper installation of the main battery shunt and ground stud connection of the main battery. The actions specified in this AD are intended to prevent such electrical power interruptions, which could result in loss of battery power to the source of standby power for the airplane.
95-06-52: 95-06-52 DORNIER: Amendment 39-9189. Docket 95-NM-33-AD. Applicability: Model 328-100 series airplanes, serial numbers 3005 through 3033 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (b) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD. Compliance: Required as indicated, unless accomplished previously. To prevent ingestion of ice into an engine, which could result in engine power rollback/flameout, accomplish the following: (a) Prior to further flight into known or forecast icing conditions, remove the bypass outlet plate having part number (P/N) 001A716A2002000 or P/N 001A716E2012000 from the lower cowlings of the engines, in accordance with Dornier Service Bulletin SB-328-71-086, dated March 6, 1995. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The removal shall be done in accordance with Dornier Service Bulletin SB-328-71-086, dated March 6, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Daimler- Benz Aerospace, Dornier, P.O. Box 1103, D-82230 Wessling, Federal Republic of Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on April 21, 1995, to all persons except those persons to whom it was made immediately effective by telegraphic AD T95-06-52, issued on March 10, 1995, which contained the requirements of this amendment.
96-19-09: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires a one-time inspection to detect cracking of the main landing gear (MLG) pistons, and repair or replacement of the pistons with new or serviceable parts, if necessary. This amendment is prompted by reports of failure of the MLG pistons that occurred during towing of the airplanes. The actions specified by this AD are intended to prevent fatigue cracking of the MLG pistons, which could result in failure of the pistons and subsequent damage to the airplane structure or injury to airplane occupants.
2022-03-20: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-8, 737-9, and 737-8200 airplanes. This AD was prompted by a determination that radio altimeters cannot be relied upon to perform their intended function if they experience interference from wireless broadband operations in the 3.7-3.98 GHz frequency band (5G C-Band), and a recent determination that, during takeoffs and landings, as a result of this interference, certain airplane systems may not properly function, resulting in longer than normal landing or rejected takeoff distances due to the effect on thrust reverser deployment, spoilers, speedbrake deployment, and increased idle thrust, regardless of the approach type or weather. This AD requires revising the limitations and operating procedures sections of the existing airplane flight manual (AFM) to incorporate limitations prohibiting the use of certain minimum equipment list (MEL) items, and to incorporate operating procedures for calculating takeoff and landing distances, when in the presence of 5G C-Band interference as identified by Notices to Air Missions (NOTAMs). The FAA is issuing this AD to address the unsafe condition on these products.
96-19-05: This amendment supersedes Airworthiness Directive (AD) 95-19-07, which currently requires the following on Fairchild Aircraft SA226 and SA227 series airplanes equipped with certain main landing gear (MLG) and nose landing gear (NLG): repetitively inspecting, using ultrasonic methods, the left-hand and right-hand MLG yokes and the NLG yokes for stress corrosion cracking, and, if any cracked yokes are found that exceed certain limits, replacing either the cracked yoke, the yoke/cylinder combination, or the affected MLG or NLG assembly. This action also supersedes priority letter AD 95-19-07 R1, which was issued to incorporate revised service information. Reports of landing gear failures on the affected airplanes prompted the original AD action. This action requires the same inspections, but requires replacing any MLG and NLG assembly with any cracks instead of allowing flight until certain crack limits are exceeded. The inability to determine or predict crack growth on areas where stress corrosion occurs on primary structure with a single-load path (MLG and NLG assemblies are considered such structure) prompted this action. The actions specified by this AD are intended to prevent MLG or NLG failure caused by stress corrosion cracking in the yokes, which could result in loss of control of the airplane during landing operations.
85-22-13: 85-22-13 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5160. Applies to Lockheed Model L-1011 series airplanes, certificated in any category. Compliance required as indicated unless previously accomplished. To prevent loss of pitch control as a result of loss of both pitch-system series trim-input bellcranks due to stress corrosion, accomplish the following: A. Within 30 days after the effective date of this AD, visually inspect both pitch- system series trim-input bellcranks in accordance with Lockheed Service Bulletin 093-27-290 dated September 23, 1985, or later FAA-approved revision: 1. If no cracks are found, reinspect in accordance with paragraph A., above, at intervals not to exceed 8 months. 2. If only one bellcrank is cracked, the airplane may remain in service if: a. There is no obvious damage or cracks outside the inspection area, as defined by Figure 1, Sheet 2 of Lockheed Service Bulletin 093-27-290, dated September 23, 1985, or later FAA-approved revision; and b. At intervals not to exceed 10 days, both bellcranks are reinspected in accordance with paragraph A., above; and c. Within 90 days after discovery of the cracked bellcrank, the torque-tube assembly is replaced. 3. If all of the conditions set forth in paragraph A.2., above, cannot be met, replace the torque-tube assembly prior to further flight. 4. If both bellcranks are cracked, replace the torque-tube assembly prior to further flight. B. The repetitive inspections required by paragraph A.1., above, may be discontinued after the torque-tube assembly is replaced by an assembly modified in accordance with Lockheed Service Bulletin 093-27-290, dated September 23, 1985, or later FAA-approved revision. C. Alternate means of compliance with this AD which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a base for accomplishment of the inspections or modifications required by this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This amendment becomes effective November 12, 1985.
96-19-01: This amendment adopts a new airworthiness directive (AD) that is applicable to Allison 250 series turbine engines. This action requires initial and repetitive visual inspections of all engine filters for metal particles resulting from premature wear of two bearings produced under Parts Manufacture Approval (PMA) by Superior Air Parts, Inc. In addition, this AD requires replacement of those bearings with bearings that incorporate improved retainers, which constitutes terminating action to the inspection requirements of this AD. This amendment is prompted by a report of a failure during a ground test of an engine with bearings manufactured by Superior Air Parts, Inc. The actions specified in this AD are intended to prevent bearing failure due to bearing separator instability, which can result in subsequent turbine and engine failure.
2011-12-51: We are adopting a new airworthiness directive (AD) for the products listed above. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires that, as of the effective date of the AD, operation of Model FALCON 7X airplanes is prohibited. This AD was prompted by a report of an uncontrolled pitch trim runaway during descent. We are issuing this AD to prevent loss of control of the airplane.
96-18-19: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-7 series airplanes, that requires repetitive non-destructive inspections to detect disbonding of fuselage skin panels, and repair, if necessary. This amendment is prompted by a report of disbonding on fuselage skin panels, which was attributed to a manufacturing process error. The actions specified by this AD are intended to prevent disbonding of the skin panels of the fuselage, which could result in degradation of the structural capability of the airplane fuselage.
62-18-02: 62-18-02 GENERAL DYNAMICS/CONVAIR: Amdt. 476 Part 507 Federal Register August 18, 1962. Applies to All Model 30 Series Aircraft. Compliance required as indicated. To preclude an unsafe condition resulting from cracking of the pylon forward engine thrust beacon channels, P/N's 30-24011-71 and -72, accomplish the following: (a) Within the next 50 hours' time in service following the effective date of this AD unless already accomplished within the last 50 hours' time in service, and thereafter at periods not to exceed 100 hours' time in service from the last inspection, conduct a close visual inspection of channels P/N's 30-24011-71 and -72 for any evidence of cracking, particular attention shall be given to the area of the relief radius in the vicinity aft end of each channel. (b) A channel exhibiting a crack in the vertical web not exceeding 1 1/2 inch may be continued in service provided that the crack is stop drilled with a 1/4-inch drill and the channel is inspected thereafter at periods not to exceed 12 hours' time in service. (c) A channel which has been stop drilled in accordance with (b) and in which the crack is found at a subsequent inspection to have progressed beyond the stop drill hole, may be continued to be used for an additional 12 hours' time in service provided that it is once again stop drilled with a 1/4-inch drill and the total length of crack does not exceed 1 1/2 inch. (d) Channels exhibiting cracks in the vertical web greater than 1 1/2 inch in length or cracks which have progressed in the horizontal web, shall be replaced prior to a further flight with a new part of the same part number or with an FAA engineering approved equivalent. When a cracked channel is replaced with a new channel P/N's 30-24011-71 or -72, the new channel shall be inspected in accordance with (a) at intervals not to exceed 100 hours' time in service, and when found cracked, shall be subject to the provisions of (b) and (c). (e) The repetitive inspections required by this AD may be discontinued on replacement channels described in Part B of General Dynamics/Convair Alert Service Bulletin A54-4 or equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. (f) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. (General Dynamics/Convair Alert Service Bulletin A54-4 for the Model 30 covers this same subject.) This directive effective August 23, 1962.
88-09-05 R1: 88-09-05 R1 DE HAVILLAND, INC.: Amendment 39-9745. Docket 95-NM-266-AD. Revises AD 88-09-05, Amendment 39-5908. Applicability: Model DHC-8 series airplanes, serial numbers 3 through 79 inclusive, on which Modification 8/0757 has not been installed; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent inadvertent opening of the airstair door and consequent depressurization of the airplane, accomplish the following: (a) Within 60 days after June 10, 1988 (the effective date of AD 88-09-05, amendment 39-5908), replace the labels marking the location and means of opening the lavatory, in accordance with the Accomplishment Instructions of de Havilland Service Bulletin 8-11-14, Revision `A', dated July 31, 1987; or Revision `B', dated July 1, 1988, or Revision `C', dated September 29, 1995. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with de Havilland Service Bulletin 8- 11-14, Revision `A', dated July 31, 1987; or de Havilland Service Bulletin 8-11-14, Revision `B', dated July 1, 1988; or de Havilland Service Bulletin 8-11-14, Revision `C', dated September 29, 1995. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Bombardier, Inc., Bombardier Regional Aircraft Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, Engine and Propeller Directorate, 10 Fifth Street, Third Floor, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on October 21, 1996.